WO2012095602A1 - Procédé de réparation d'au moins une partie d'un panneau acoustique pour une nacelle - Google Patents
Procédé de réparation d'au moins une partie d'un panneau acoustique pour une nacelle Download PDFInfo
- Publication number
- WO2012095602A1 WO2012095602A1 PCT/FR2012/050061 FR2012050061W WO2012095602A1 WO 2012095602 A1 WO2012095602 A1 WO 2012095602A1 FR 2012050061 W FR2012050061 W FR 2012050061W WO 2012095602 A1 WO2012095602 A1 WO 2012095602A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- acoustic
- skin
- cells
- panel
- cut
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 38
- 230000001413 cellular effect Effects 0.000 claims abstract description 28
- 239000011347 resin Substances 0.000 claims abstract description 27
- 229920005989 resin Polymers 0.000 claims abstract description 27
- 239000007787 solid Substances 0.000 claims abstract description 14
- 238000002347 injection Methods 0.000 claims description 9
- 239000007924 injection Substances 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 6
- 239000012815 thermoplastic material Substances 0.000 claims description 6
- 239000004744 fabric Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 3
- 210000004027 cell Anatomy 0.000 description 57
- 239000002245 particle Substances 0.000 description 11
- 238000010521 absorption reaction Methods 0.000 description 4
- 238000004140 cleaning Methods 0.000 description 3
- 210000003850 cellular structure Anatomy 0.000 description 2
- 230000001627 detrimental effect Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000006116 polymerization reaction Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 239000012943 hotmelt Substances 0.000 description 1
- YAFQFNOUYXZVPZ-UHFFFAOYSA-N liproxstatin-1 Chemical compound ClC1=CC=CC(CNC=2C3(CCNCC3)NC3=CC=CC=C3N=2)=C1 YAFQFNOUYXZVPZ-UHFFFAOYSA-N 0.000 description 1
- 239000003960 organic solvent Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
- Y10T156/1082—Partial cutting bonded sandwich [e.g., grooving or incising]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49398—Muffler, manifold or exhaust pipe making
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49616—Structural member making
- Y10T29/49618—Restoring existing member, e.g., reinforcing, repairing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49718—Repairing
- Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49718—Repairing
- Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
- Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
Definitions
- the present invention relates to a method for repairing at least a portion of an acoustic panel for a nacelle of a turbojet engine of an aircraft, said panel comprising an acoustic skin pierced with a plurality of acoustic holes, a solid skin and an acoustic structure comprising a plurality of cellular cells each having one or more drainage holes disposed in one or more walls forming each cellular cell, the said structure being disposed between the acoustic skin and the solid skin.
- the invention also relates to an acoustic panel repaired by such a method.
- Aircraft turbojets generate significant noise pollution. There is a strong demand to reduce this pollution, especially as the turbojets used become more and more powerful.
- the design of the nacelle surrounding a turbojet contributes to a large extent to the reduction of this noise pollution.
- nacelles are equipped with acoustic panels to reduce the noise due to the circulation of air flows through the turbojet engine and vibrations of the structures of the nacelle.
- Acoustic panels are sandwich structures well known for absorbing these noises. These panels usually comprise an acoustic cellular structure which may be in the form of one or more superimposed alveolar layers and each comprising honeycomb cells (commonly called “honeycomb” structure).
- the cellular acoustic structure is generally coated on the so-called outer face, that is to say the furthest radially from the axis of the engine, of a skin impermeable to air, called “full”, and on the face internal, that is to say the radially closest to the axis of the engine, a perforated skin permeable to air, called “acoustic”.
- the acoustic panel is then assembled by arranging and then gluing the various skins and the acoustic structure on a mold to the required shape. The whole is baked in an autoclave so as to clamp the layers and to polymerize the adhesives.
- Such panels are acoustic resonators capable of "trapping" the noise and thus to reduce noise emissions towards the outside of the nacelle.
- Such acoustic panels may be damaged during operation of the nacelle, requiring the repair or replacement of one or all of said panels.
- the visible and accessible parts of the acoustic panel area to be repaired are cleaned before any repair is done. Indeed, polluting particles from the turbojet engine environment are deposited on said visible and accessible parts during operation of the turbojet engine. The presence of such particles is detrimental to the perenniality of the future repaired panel.
- An object of the present invention is to provide a repair method that meets this need which is effective and simple to implement.
- the subject of the invention is a method for repairing at least part of an acoustic panel for a nacelle of a turbojet engine of an aircraft, said panel comprising an acoustic skin pierced with a plurality of acoustic holes, a solid skin and an acoustic cellular structure comprising a plurality of cellular cells each having one or more drainage orifices arranged in one or more walls forming each cellular cell, said structure being disposed between the acoustic skin and full skin,
- said method comprising the steps of:
- B - the said part is cut with the exception of the acoustic skin;
- C- said cut portion is removed thereby forming a cutting in the cut acoustic panel forming a cutting zone which is closed by the acoustic skin;
- D - a curable resin is injected at ambient temperature through acoustic holes of the acoustic skin, said holes ending in entire cellular cells adjacent to junction cells belonging to the acoustic panel cut so as to obstruct the drainage orifices of said cells; alveolar junction, said junction cells being intended to be in contact with the cutting zone;
- a solid replacement skin is formed on the replacement cellular acoustic structure.
- ambient temperature here means the temperature of the repair site where the acoustic panel to be repaired is placed.
- the method of the invention advantageously makes it possible to block the flow of air during the repair of the acoustic panel between the repair zone and the periphery of the latter.
- the method of the invention thus allows a simple and effective way to avoid the entrainment of pollutant particles in the area of the acoustic panel to repair which ensures good cohesion of the future repaired panel.
- the method of the invention does not advantageously increase the mass of the acoustic panel thus repaired.
- the method of the invention does not substantially penalize the acoustic properties of said acoustic panel. Indeed, the number of clogged alveolar cells is negligible relative to the number of total alveolar cells.
- the method according to the invention comprises one or more of the following optional characteristics considered alone or according to all the possible combinations:
- the resin used is chosen from the materials composing the acoustic panel or the thermoplastic materials;
- step D the resin is injected by means of an injection means, in particular a pneumatic gun or a syringe, which allows a simple and reliable injection; in which during step B, the portion is cut so that the cutting zone is delimited by a cutting line disposed at a distance of between 2 mm and 3 mm from the vertices of each nearest junction cell. of the cutting line, which allows a regular cutting line and thus an injection of the resin controlled for the user;
- the method of the invention comprises an additional step G at the end of step F in which the adjacent open cells alveolar cells obstructed by the resin, which optimizes the acoustic absorption of the acoustic panel;
- step G said cells are unblocked by means of heating and then of a means of disengagement which makes it possible to unobstructed in a simple and reliable manner the adjacent alveolar cells;
- the full replacement skin is formed by the application of pre-impregnated tissues, which makes it possible to obtain, in a simple and reliable manner, a full replacement skin;
- the cellular acoustic structure comprises one or more alveolar layers substantially superimposed and separated or not by a septum, which makes it possible to improve the acoustic absorption of the acoustic panel.
- the subject of the invention is an acoustic panel repaired by the repair method according to the invention.
- FIG. 1 is a partial schematic section of an embodiment of a nacelle of the invention
- FIG. 2 is a perspective view of a cut acoustic panel according to one embodiment of the method of the invention
- FIG. 3 is an enlarged perspective view of zone III of FIG. 2;
- FIG. 4 is a schematic cross section of an adjacent solid cell during resin injection according to one embodiment of the method of the invention.
- a nacelle 1 has a substantially tubular shape along a longitudinal axis ⁇ .
- the nacelle of the invention 1 comprises an upstream section 2 with an inlet lip 1 3 of air forming an inlet of a ir 3, a median section 4 surrounding a fan 5 of a turbojet engine 6 and a downstream section 7.
- the downstream section 7 comprises a fixed internal structure 8 (I FS) surrounding the upstream portion of the turbojet engine 6, a fixed external structure (OFS) 9 and a movable cowl (not shown) comprising thrust reversal means.
- the IFS 8 and OFS 9 delimits an annular vein 10 allowing the passage of a main air flow 12 penetrating the nacelle 1 of the invention at the level of the air inlet 3.
- the nacelle of the invention 1 therefore comprises walls delimiting a space, such as the air inlet 3 or the annular vein 10, in which the main air flow 12 enters, circulates and is ejected.
- the nacelle 1 of the invention ends with an ejection nozzle 21 comprising an external module 22 and an internal module 24.
- the internal and external modules 24 24 define a flow channel of a hot air flow 25 exiting turbojet engine 6.
- Each wall in contact with the hot and cold air streams 12 may be formed of one or more acoustic panels.
- a pa nn ea u acou s s tic typically comprises an acoustic skin pierced with a plurality of acoustic holes, a solid skin and at least one layer of acoustic structure comprising a plurality of cellular cells each of which comprises one or more drainage holes in one or more walls forming a honeycomb cell.
- the acoustic structure may be formed in whole or in part of a single acoustic layer made of cellular cells.
- the acoustic structure may be formed in whole or in part from a plurality of acoustic layers consisting of alveolar cells separated or not by a septum.
- the acoustic structure layer or layers are arranged between the acoustic skin and the solid skin.
- the method of the invention makes it possible to repair such an acoustic panel.
- Said method comprises the steps where: A-delimit a part of the acoustic panel to be cut;
- D- a curable resin is injected at ambient temperature through acoustic holes of the acoustic skin, said holes ending in whole cellular cells adjacent to junction cells belonging to the acoustic panel cut so as to obstruct the drainage orifices of said cells junction, said junction cell cells being intended to be in contact with the cutting zone and also the peripheral honeycomb cells belonging to the replacement part of the acoustic panel;
- a solid replacement skin is formed on the replacement cellular acoustic structure.
- the method of the invention advantageously makes it possible to block the flow of air during the repair of the acoustic panel between the repair zone and the periphery of the latter.
- the method of the invention thus makes it possible in a simple and effective way to eliminate the pollution of the cutting zone by particles derived in particular from the environment of the turbojet engine 6 and which are present in the entire cellular cells adjacent to the cutting zone. Such pollution is detrimental to the cohesion of the acoustic panel thus repaired.
- the drainage holes of junction cell cells in contact with the cutting line and the adjacent whole cell cells are obstructed. As a result, the polluting particles can no longer be conveyed through these orifices or adjacent whole cells. Everything happens as if a protective barrier against the polluting particles of the acoustic panel is formed.
- the method of the invention does not increase or not the mass of the acoustic panel repaired and does not penalize or very little acoustic properties of the latter. Indeed, the number of cells Clogged alveolar cells are negligible compared to the number of total alveolar cells. Similarly, the acoustic absorption function of the acoustic panel remains substantially the same as it was before repair.
- step A where a part of the acoustic panel to be cut is defined can be realrise by marking on the full skin, for example.
- Said step A may be preceded by a step of cleaning the acoustic panel, in particular visible and accessible parts such as solid skin, by means of a jet of water under pressure, for example.
- Step B where said part is cut except the acoustic skin is made with a cutting means.
- cutting means there may be mentioned a means of a drill equipped with a disc of diameter substantially equal to 30 mm diamond blade.
- step C the cut portion is removed thereby forming the cutting zone in the cut acoustic panel, said cutting zone being closed at one end by the acoustic skin.
- the cut portion can be removed manually or automatically.
- a cleaning step can be performed.
- Said cleaning step can be carried out by an organic solvent associated with a lint-free means for wiping said solvent and heating in an oven.
- the dust particles resulting from cutting are removed from the solid skin and a portion of the alveolar cells.
- the acoustic panel is advantageously degreased. The presence of grease would penalize the cohesion of the panel thus repaired.
- FIGS 2 and 3 illustrate a panel 1 00 thus cut.
- Said panel 1 00 has a cutting zone 102 covered by the acoustic skin 1 04.
- the acoustic skin 1 04 typically comprises a plurality of acoustic holes 106 whose diameter is between 1 mm and 2 mm.
- the cutting zone 102 is formed by the cut-out part of the acoustic panel, said part being able to have any suitable shape and dimension.
- the acoustic acoustic structure 108 of the cut acoustic panel comprises a plurality of cellular cells 1 10.
- the cellular acoustic structure 108 consists of a single alveolar layer itself constituted by cellular cells 10.
- Said cells 1 10 are of hexagonal shape in the mode embodiment shown in Figures 2 and 3.
- Said cellular cells 1 10 may be of any other form adapted to the invention.
- the cellular acoustic structure 108 is covered with a full skin 12 shown in transparency for the purposes of FIG.
- Acoustic skin 104 and full 1 1 2 can be made by superposition of prepreg fabrics cooked in an autoclave or at atmospheric pressure.
- step B it is possible to cut out the portion of the full skin 1 12 and the cellular acoustic structure 108 to be replaced so that the cutting zone 102 comprises a line of FIG. cutout 120 disposed at a distance di and 02 between 2 mm and 3 mm from the vertices 1 21 of junction cells 122 closest to said cutting line 120.
- the cutting line 120 is more regular. This induces an injection of the resin 130 by the user easier for the user and managed just as necessary to avoid any excess of said resin 130.
- junction cells are in contact at both the cutting line 120 and adjacent adjacent cellular cells 124.
- the junction cells 122 are further intended to be in contact with the peripheral alveolar cells belonging to the portion of the alveolar junction cell 122. replacement at the cutting area 102.
- a curable resin 130 is injected at room temperature through acoustic holes 106 of the acoustic skin 104, said holes 106 terminating in the adjacent whole cell cells 124 of so as to obstruct the drainage orifices 132 of the junction cells 122 in contact with the adjacent cellular cells 124.
- the ambient temperature is between 15 ° C and
- each adjacent full cell cell 124 and drainage holes 132 are filled with curable resin at room temperature.
- the polymerization at ambient temperature of the resin advantageously allows the user to visually ensure that the drain holes 132 are well sealed before engaging the steps of replacing the cut portion.
- the filling of said drainage orifices 132 makes it possible to prevent the circulation of the polluting particles towards the cutting zone of the acoustic panel to be repaired.
- the resin used may be chosen from the materials composing the acoustic panel or the thermoplastic materials.
- the latter can be hot melt.
- the use of a thermoplastic material advantageously makes it possible to be removable from the acoustic panel after repair.
- the resin can be injected by means of an injection means, in particular a pneumatic gun or a syringe which allows a simple and reliable intervention on the acoustic panel 100 wherever the operator has access.
- an injection means in particular a pneumatic gun or a syringe which allows a simple and reliable intervention on the acoustic panel 100 wherever the operator has access.
- Injection of the resin may be carried out in adjacent integral cells 124 arranged in staggered rows 140 or along a line 142, as shown in FIG. 6.
- the staggered or in-line arrangement depends on the orientation of the adjacent whole cell cells. 124.
- step E there is placed on the acoustic skin 104 a replacement cellular acoustic structure in the cutting zone 102, said replacement acoustic structure being of dimension substantially equal to that of the cutting.
- step F a full replacement skin is formed on the replacement honeycomb acoustic structure.
- the full replacement skin can be formed by the application of prepreg fabrics.
- the cohesion of the pre-impregnated fabrics can be done in an autoclave in which is disposed the repaired panel.
- the cohesion of the preimpregnated fabrics is at atmospheric pressure.
- the method of the invention may comprise an additional step G at the end of step F in which the junction alveolar cells 122 and the adjacent adjacent alveolar cells 124 obstructed by the resin are uncapped. 130.
- step G the acoustic absorption of the acoustic panel is improved.
- step G it is possible to unblock said cellular cells 122 and 124 by means of heating and then a means of clearance, especially in the case of a resin comprising a thermoplastic material.
- a resin comprising a thermoplastic material.
- it can be heated to a heating temperature of between 1 90 ° C and the maximum temperature beyond which the acoustic panel is damaged.
- a heating temperature mention may be made of approximately 220 ° C.
- the resin 130 is removed by the release means such as suction means. Resin 130 may also be removed by other suitable means.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112013016130A BR112013016130A2 (pt) | 2011-01-13 | 2012-01-10 | método para reparar pelo menos uma porção de um painel acústico para uma nacela de um motor turbojato de aeronave e painel acústico. |
CA2823857A CA2823857A1 (fr) | 2011-01-13 | 2012-01-10 | Procede de reparation d'au moins une partie d'un panneau acoustique pour une nacelle |
ES12702306.7T ES2531849T3 (es) | 2011-01-13 | 2012-01-10 | Procedimiento de reparación de por lo menos una parte de un panel acústico para una góndola |
EP12702306.7A EP2663449B1 (fr) | 2011-01-13 | 2012-01-10 | Procédé de réparation d'au moins une partie d'un panneau acoustique pour une nacelle |
RU2013137075/05A RU2013137075A (ru) | 2011-01-13 | 2012-01-10 | Способ ремонта по меньшей мере участка звукопоглощающей панели для гондолы |
CN201280005072.4A CN103313842B (zh) | 2011-01-13 | 2012-01-10 | 用于修理发动机舱的声学板的至少一部分的方法 |
US13/941,044 US8636107B2 (en) | 2011-01-13 | 2013-07-12 | Method for repairing at least a portion of an acoustic panel |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1150284A FR2970433B1 (fr) | 2011-01-13 | 2011-01-13 | Procede de reparation d'au moins une partie d'un panneau acoustique pour une nacelle |
FR11/50284 | 2011-01-13 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/941,044 Continuation US8636107B2 (en) | 2011-01-13 | 2013-07-12 | Method for repairing at least a portion of an acoustic panel |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012095602A1 true WO2012095602A1 (fr) | 2012-07-19 |
Family
ID=44318528
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/050061 WO2012095602A1 (fr) | 2011-01-13 | 2012-01-10 | Procédé de réparation d'au moins une partie d'un panneau acoustique pour une nacelle |
Country Status (9)
Country | Link |
---|---|
US (1) | US8636107B2 (fr) |
EP (1) | EP2663449B1 (fr) |
CN (1) | CN103313842B (fr) |
BR (1) | BR112013016130A2 (fr) |
CA (1) | CA2823857A1 (fr) |
ES (1) | ES2531849T3 (fr) |
FR (1) | FR2970433B1 (fr) |
RU (1) | RU2013137075A (fr) |
WO (1) | WO2012095602A1 (fr) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2953812B1 (fr) * | 2009-12-11 | 2012-09-07 | Airbus Operations Sas | Procede de reparation d'un fuselage d'aeronef |
EP2961967B1 (fr) * | 2013-03-01 | 2021-03-31 | Raytheon Technologies Corporation | Réparation de détérioration superficielle au niveau des arêtes de panneaux cellulaires |
US10800117B2 (en) * | 2015-03-12 | 2020-10-13 | Rohr, Inc. | Method of forming an acoustic bond panel with insertable acoustic assemblies |
US10040535B2 (en) * | 2015-12-02 | 2018-08-07 | Embraer S.A. | Composite accoustical panels especially useful for interior panel assemblies of aircraft passenger cabins |
CN110087868B (zh) * | 2016-12-20 | 2021-10-22 | 罗尔公司 | 声学性质得以保留的机器视觉声学面板修复 |
US10676171B2 (en) * | 2017-08-18 | 2020-06-09 | Rohr, Inc. | Structural panel with splice joint between adjacent core structures |
US10671047B2 (en) * | 2018-03-15 | 2020-06-02 | The Boeing Company | Composite structure repair system and method |
US11286859B2 (en) | 2018-08-09 | 2022-03-29 | General Electric Company | Acoustic panel and method for making the same |
FR3088848B1 (fr) * | 2018-11-28 | 2020-12-04 | Airbus Operations Sas | Procédé de fabrication d’un élément acoustique d’une structure d’absorption acoustique à partir d’au moins une feuille de matière |
CN112693622B (zh) * | 2020-12-29 | 2023-09-05 | 中国航空工业集团公司西安飞机设计研究所 | 一种飞机翼面抽钉松动修理方法 |
FR3128778A1 (fr) * | 2021-11-04 | 2023-05-05 | Airbus Operations | Module assurant une atténuation d’ondes acoustiques et un échange thermique |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1870228A1 (fr) * | 2006-06-19 | 2007-12-26 | United Technologies Corporation | Réparation de structures sandwich composites |
EP1985538A2 (fr) * | 2007-04-24 | 2008-10-29 | United Technologies Corporation | Utilisation d'un renfort pour réparer une pièce d'un moteur d'avion |
EP2108504A1 (fr) * | 2008-04-11 | 2009-10-14 | United Technologies Corporation | Renfort métallique pour la réparation d'une pièce de moteur à turbine à gaz |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4257998A (en) * | 1978-05-01 | 1981-03-24 | The Boenig Company | Method of making a cellular core with internal septum |
US4517038A (en) * | 1983-05-10 | 1985-05-14 | Miller Robert W | Method of repairing ballistic damage |
US4668317A (en) * | 1984-06-01 | 1987-05-26 | The United States Of America As Represented By The Secretary Of The Air Force | Damaged radar radome repair method |
US4855182A (en) * | 1986-10-03 | 1989-08-08 | Isovolta Osterreichische Isolierstoffwerke Aktiengesellschaft | Repair laminate |
US5041323A (en) * | 1989-10-26 | 1991-08-20 | Rohr Industries, Inc. | Honeycomb noise attenuation structure |
GB9014381D0 (en) * | 1990-06-28 | 1990-08-22 | Short Brothers Plc | A composite structural component |
US5653836A (en) * | 1995-07-28 | 1997-08-05 | Rohr, Inc. | Method of repairing sound attenuation structure used for aircraft applications |
US5958166A (en) * | 1996-12-31 | 1999-09-28 | Mcdonnell Douglas Corporation | Method for repairing high temperature composite structures |
US6173807B1 (en) * | 1998-04-13 | 2001-01-16 | The Boeing Company | Engine nacelle acoustic panel with integral wedge fairings and an integral forward ring |
US7069830B1 (en) * | 2000-06-19 | 2006-07-04 | The United States Of America As Represented By The Secretary Of The Air Force | Surface repair method and tool therefor |
US6656299B1 (en) * | 2001-12-19 | 2003-12-02 | Lockheed Martin Corporation | Method and apparatus for structural repair |
US7572347B2 (en) * | 2006-05-26 | 2009-08-11 | United Technologies Corporation | Repair of composite sandwich structures with uneven bond surfaces |
US8592024B2 (en) * | 2006-05-26 | 2013-11-26 | United Technologies Corporation | Repair of perforated acoustic skins by reverse pin transfer molding |
US20080233346A1 (en) * | 2007-03-23 | 2008-09-25 | United Technologies Corporation | Repair of a composite sandwich structure having a perforated skin |
FR2971613B1 (fr) * | 2011-02-10 | 2013-03-15 | Airbus Operations Sas | Panneau pour le traitement acoustique comprenant une jonction entre deux parties et procede de reparation d'un panneau pour le traitement acoustique |
-
2011
- 2011-01-13 FR FR1150284A patent/FR2970433B1/fr not_active Expired - Fee Related
-
2012
- 2012-01-10 WO PCT/FR2012/050061 patent/WO2012095602A1/fr active Application Filing
- 2012-01-10 RU RU2013137075/05A patent/RU2013137075A/ru not_active Application Discontinuation
- 2012-01-10 CA CA2823857A patent/CA2823857A1/fr not_active Abandoned
- 2012-01-10 BR BR112013016130A patent/BR112013016130A2/pt not_active IP Right Cessation
- 2012-01-10 ES ES12702306.7T patent/ES2531849T3/es active Active
- 2012-01-10 EP EP12702306.7A patent/EP2663449B1/fr not_active Not-in-force
- 2012-01-10 CN CN201280005072.4A patent/CN103313842B/zh not_active Expired - Fee Related
-
2013
- 2013-07-12 US US13/941,044 patent/US8636107B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1870228A1 (fr) * | 2006-06-19 | 2007-12-26 | United Technologies Corporation | Réparation de structures sandwich composites |
EP1985538A2 (fr) * | 2007-04-24 | 2008-10-29 | United Technologies Corporation | Utilisation d'un renfort pour réparer une pièce d'un moteur d'avion |
EP2108504A1 (fr) * | 2008-04-11 | 2009-10-14 | United Technologies Corporation | Renfort métallique pour la réparation d'une pièce de moteur à turbine à gaz |
Also Published As
Publication number | Publication date |
---|---|
US8636107B2 (en) | 2014-01-28 |
EP2663449A1 (fr) | 2013-11-20 |
RU2013137075A (ru) | 2015-02-20 |
FR2970433A1 (fr) | 2012-07-20 |
FR2970433B1 (fr) | 2013-01-04 |
EP2663449B1 (fr) | 2014-12-17 |
US20130292202A1 (en) | 2013-11-07 |
BR112013016130A2 (pt) | 2018-07-10 |
CN103313842A (zh) | 2013-09-18 |
CN103313842B (zh) | 2015-12-02 |
CA2823857A1 (fr) | 2012-07-19 |
ES2531849T3 (es) | 2015-03-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2663449B1 (fr) | Procédé de réparation d'au moins une partie d'un panneau acoustique pour une nacelle | |
EP2250357B1 (fr) | Structure d'entree d'air pour une nacelle d'un aeronef | |
EP2321510B1 (fr) | Structure d'entrée d'air de nacelle de turboréacteur à dégivrage pneumatique | |
EP2291840B1 (fr) | Panneau acoustique pour une tuyère d'éjection | |
EP1999020B1 (fr) | Structure pour levre d'entree d'air de nacelle a degivrage electrique comprenant une zone d'attenuation acoustique | |
EP2132730B1 (fr) | Procede de realisation d'une structure acoustiquement resistive, structure acoustiquement resistive ainsi obtenue et revetement utilisant une telle structure | |
EP2763892B1 (fr) | Procédé de fabrication d'un panneau d'absorption acoustique | |
EP2580121B1 (fr) | Nacelle de turboreacteur | |
EP3325271B1 (fr) | Panneau d'atténuation acoustique en matériau composite céramique oxyde avec âme en matériau métallique converti électrochimiquement | |
WO2009077688A2 (fr) | Nacelle d'aeronef comprenant des moyens d'evacuation d'air chaud | |
FR2820716A1 (fr) | Procede de degivrage par circulation forcee d'un fluide, d'un capot d'entree d'air de moteur a reaction et dispositif pour sa mise en oeuvre | |
CA2761666A1 (fr) | Procede d'assemblage d'une protection thermique sur une structure interne fixe de nacelle de turboreacteur | |
WO2013186476A1 (fr) | Procédé de fabrication de panneaux cellulaires, destinés notamment au domaine de l'aéronautique | |
FR2948098A1 (fr) | Structure de bord d'attaque notamment pour entree d'air de nacelle de moteur d'aeronef | |
FR2973467A1 (fr) | Dispositif d'etancheite destine a etre dispose entre deux structures d'une nacelle | |
EP3724076B1 (fr) | Lèvre d'entrée d'air de nacelle pour turboréacteur | |
WO2016071611A1 (fr) | Procédé pour la réparation d'une peau perforée d'un panneau au moyen d'un doubleur | |
WO2015036716A1 (fr) | Procédé de réparation d'une peau d'un panneau composite | |
FR2940360A1 (fr) | Panneau d'attenuation acoustique pour nacelle de moteur d'aeronef,structure d'entree d'air et structure interne fixe incorporant ledit panneau | |
WO2016092238A1 (fr) | Procédé pour la réparation d'un panneau acoustique en matériau composite | |
WO2015001258A1 (fr) | Procédé de réparation d'un panneau par application d'un doubleur | |
FR3044961A1 (fr) | Panneau pour nacelle de turboreacteur comportant une protection thermique et procede de fabrication d’un tel panneau | |
FR3032966A1 (fr) | Panneau d’attenuation acoustique en materiau composite a matrice ceramique et a ame metallique |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 12702306 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2823857 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012702306 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2013137075 Country of ref document: RU Kind code of ref document: A |
|
REG | Reference to national code |
Ref country code: BR Ref legal event code: B01A Ref document number: 112013016130 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: 112013016130 Country of ref document: BR Kind code of ref document: A2 Effective date: 20130624 |